U.S. patent number 7,344,354 [Application Number 11/222,101] was granted by the patent office on 2008-03-18 for methods and apparatus for operating gas turbine engines.
This patent grant is currently assigned to General Electric Company. Invention is credited to Steven Mark Ballman, David Lawrence Bedel, Andrew John Lammas, Sean Patrick McGowan, Daniel Edward Wines.
United States Patent |
7,344,354 |
Lammas , et al. |
March 18, 2008 |
**Please see images for:
( Certificate of Correction ) ** |
Methods and apparatus for operating gas turbine engines
Abstract
A method of assembling a gas turbine engine that includes
providing a rotor assembly including a rotor shaft, an air duct,
and a rotor disk that includes a mounting arm, wherein the mounting
arm extends radially inward from the rotor disk towards the rotor
shaft and coupling a rotor impeller assembly to the mounting arm,
wherein the rotor impeller assembly includes a carrier and a
plurality of bleed tubes that each extend outwardly from the
carrier and are configured to receive bleed air.
Inventors: |
Lammas; Andrew John
(Maineville, OH), Ballman; Steven Mark (West Chester,
OH), Wines; Daniel Edward (Cincinnati, OH), Bedel; David
Lawrence (Oldenburg, IN), McGowan; Sean Patrick
(Cincinnati, OH) |
Assignee: |
General Electric Company
(Schenectady, NY)
|
Family
ID: |
37830195 |
Appl.
No.: |
11/222,101 |
Filed: |
September 8, 2005 |
Prior Publication Data
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Document
Identifier |
Publication Date |
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US 20070053770 A1 |
Mar 8, 2007 |
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Current U.S.
Class: |
415/115;
29/889.2; 416/97R |
Current CPC
Class: |
F01D
5/081 (20130101); F04D 29/321 (20130101); F05D
2230/60 (20130101); F05D 2260/602 (20130101); F04D
27/023 (20130101); Y10T 29/4932 (20150115) |
Current International
Class: |
F01D
9/06 (20060101) |
Field of
Search: |
;415/115,116,119
;29/889.2 |
References Cited
[Referenced By]
U.S. Patent Documents
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3844110 |
October 1974 |
Widlansky et al. |
5143512 |
September 1992 |
Corsmeier et al. |
5472313 |
December 1995 |
Quinones et al. |
6183195 |
February 2001 |
Tremaine |
6382903 |
May 2002 |
Caruso et al. |
6397604 |
June 2002 |
Eldrid et al. |
6435812 |
August 2002 |
DeStefano et al. |
6450758 |
September 2002 |
Schmidt |
6464461 |
October 2002 |
Wilson et al. |
6477773 |
November 2002 |
Wilson et al. |
6506021 |
January 2003 |
Wilson et al. |
6648592 |
November 2003 |
Escure et al. |
7086830 |
August 2006 |
Fitzgerald et al. |
|
Primary Examiner: Look; Edward K.
Assistant Examiner: Hanan; Devin
Attorney, Agent or Firm: Andes; William Scott Armstrong
Teasdale LLP
Claims
What is claimed is:
1. A method of assembling a gas turbine engine, said method
comprising: providing a rotor assembly including a rotor shaft, an
air duct, and a rotor disk that includes a mounting arm that
extends radially inward from the rotor disk towards the rotor
shaft; and coupling a rotor impeller assembly to the mounting arm,
wherein the rotor impeller assembly includes a cater and a
plurality of bleed tubes that each extend outwardly from the
carrier and are configured to receive bleed air, said coupling a
rotor impeller assembly to the mounting arm further comprising
coupling the rotor impeller assembly such that the carrier is
positioned radially inward from the at least one rotor disk.
2. A method in accordance with claim 1 wherein coupling a rotor
impeller assembly to the mounting arm further comprises coupling
the rotor impeller assembly to the mounting arm by an annular
coupling nut.
3. A method in accordance with claim 2 wherein coupling a rotor
impeller assembly to the mounting arm further comprises coupling
the rotor impeller assembly to the mounting arm such that the
coupling nut substantially seals with the air duct.
4. A method in accordance with claim 1 wherein coupling a rotor
impeller assembly to the mounting arm further comprises coupling
the rotor impeller assembly to the mounting arm such that the
plurality of bleed tubes are each positioned in flow communication
with the air duct.
5. A method in accordance with claim 1 wherein coupling a rotor
impeller assembly to the mounting arm further comprises coupling
the rotor impeller assembly cater to the mounting arm without
utilizing any bolt openings formed within the carrier.
6. A method in accordance with claim 1 wherein providing a rotor
assembly including a rotor disk further comprises coupling the
plurality of bleed tubes to the carrier such that the bleed tubes
extend radially outward from and are spaced circumferentially
around the carrier.
7. A rotor assembly for a gas turbine engine including a centerline
axis of rotation, said rotor assembly comprising: a rotor shaft; at
least one rotor disk coupled to said rotor shaft and comprising an
integral mounting arm extending radially inward towards said rotor
shaft; and a rotor impeller assembly coupled to said mounting arm,
and said rotor impeller assembly and comprising a carrier that is
radially inward from said at least one rotor disk and a plurality
of bleed tubes extending radially outward from said carrier, each
of said plurality of bleed tubes configured to receive bleed
air.
8. A rotor assembly in accordance with claim 7 wherein said carrier
circumscribes said rotor shaft and comprises a first portion, a
second portion, and a third portion, said first portion coupled to
said mounting arm to secure said rotor assembly thereto, said
second portion coupled in sealing arrangement with an air duct
extending along said rotor shaft, said third portion coupled to
said plurality of bleed tubes.
9. A rotor assembly in accordance with claim 7 wherein said carrier
further comprises a plurality of openings circumferentially-spaced
around said cater in flow communication with said plurality of
bleed tubes.
10. A rotor assembly in accordance with claim 7 wherein said
mounting arm further comprises an arm portion extending radially
inward towards said rotor shaft and an attachment portion extending
substantially parallel to said rotor shaft, said attachment portion
is coupled to said carrier by an annular coupling nut.
11. A rotor assembly in accordance with claim 7 wherein said
carrier is coupled to said at least one rotor disk without
utilizing any bolt openings formed within the carrier.
12. A gas turbine engine comprising a rotor assembly comprising a
rotor shaft, at least one rotor disk, and a rotor impeller
assembly, said at least one rotor disk coupled to said rotor shaft
and comprising a mounting arm, said rotor impeller assembly coupled
to said mounting arm, and said rotor impeller assembly and
comprising a carrier that is radially inward from said at least one
rotor disk and a plurality of bleed tubes extending radially
outward from said carrier, each of said plurality of bleed tubes
configured to receive bleed air.
13. A gas turbine engine in accordance with claim 12 wherein said
rotor impeller assembly further comprises an annular coupling nut,
said annular coupling nut is radially inward from said at least one
rotor disk and configured to couple said carrier to said mounting
arm.
14. A gas turbine engine in accordance with claim 13 wherein said
mounting aim further comprises an arm portion extending radially
inward towards said rotor shaft and an attachment portion extending
substantially parallel to said rotor shaft, said attachment portion
is coupled to said carrier by said annular coupling nut.
15. A gas turbine engine in accordance with claim 12 wherein said
carrier circumscribes said rotor shaft and comprises a first
portion, a second portion, and a third portion, said first portion
coupled to said mounting arm to secure said rotor assembly thereto,
said second portion coupled in sealing arrangement with an air duct
extending along said rotor shaft, said third portion coupled to
said plurality of bleed tubes.
16. A gas turbine engine in accordance with claim 12 wherein said
carrier further comprises a plurality of openings
circumferentially-spaced around said carrier in flow communication
with said plurality of bleed tubes.
17. A gas turbine engine in accordance with claim 12 wherein said
carrier has a low profile such that said carrier facilitates
positioning said rotor impeller assembly at a desired location
within said rotor assembly.
18. A gas turbine engine in accordance with claim 12 wherein said
carrier is to said at least one rotor disk without utilizing any
bolt openings formed within the carrier.
Description
BACKGROUND OF THE INVENTION
This application relates generally to gas turbine engines and, more
particularly, to gas turbine engine rotor impeller assemblies.
At least some known gas turbine engines include a multi-stage axial
compressor, a combustor, and a turbine coupled together in a serial
flow arrangement. Airflow entering the compressor is compressed and
directed to the combustor where the air is mixed with fuel and
ignited, producing hot combustion gases used to drive the turbine.
To facilitate cooling components exposed to heat transfer hot
combustion gases entering the turbine, at least some known gas
turbine engines channel cooling air towards the turbine and
associated components.
Compressor bleed air is often used as a source of cooling air for
high pressure turbine blades or is used to pressurize a sump. Some
known turbine engines include an impeller assembly that enables
cooling air to be extracted from a compressor stage at a desired
pressure and temperature. However, within known gas turbine engines
the rotor impeller assembly is coupled to the rotor at a bolted
joint that joins two adjacent stages. More specifically, in such
gas turbine engines to facilitate extraction at a desired pressure
and temperature, the bleed air is extracted only from a location in
the compressor that is generally coincident with the coupling stage
joint to enable the impeller assembly to be secured in a portion
prior to the adjacent rotor stages being coupled together. Although
such a joint enables the two stages to be coupled together, such
bolted joints are not located at the desired location to receive
bleed air at a desired pressure and temperature. Furthermore, it is
difficult to position the rotor impeller assembly because at such
bolted joints because of their location, and as such, such
impellers may increase the overall assembly time, overall weight,
and may facilitate an increase in disk wear.
BRIEF DESCRIPTION OF THE INVENTION
In one aspect, a method of assembling a gas turbine engine is
provided. The method includes providing a rotor assembly including
a rotor shaft, an air duct, and a rotor disk that includes a
mounting arm that extends radially inward from the rotor disk
towards the rotor shaft and coupling a rotor impeller assembly to
the mounting arm wherein the rotor impeller assembly includes a
carrier and a plurality of bleed tubes that each extend outwardly
from the carrier and are configured to receive bleed air.
In another aspect, a rotor assembly for a gas turbine engine is
provided. The rotor assembly includes a rotor shaft and at least
one rotor disk coupled to the rotor shaft and includes an integral
mounting arm extending radially inward towards the rotor shaft. The
assembly also includes a rotor impeller assembly coupled to the
mounting arm, the rotor impeller assembly includes a carrier and a
plurality of bleed tubes extending radially outward from the
carrier, each of the plurality of bleed tubes is configured to
receive bleed air.
In a further aspect, a gas turbine engine including a rotor
assembly is provided. The rotor assembly includes rotor shaft, at
least one rotor disk, and a rotor impeller assembly. The at least
one rotor disk is coupled to the rotor shaft and includes a
mounting arm. The rotor impeller assembly is coupled to the
mounting arm, the rotor impeller assembly includes a carrier and a
plurality of bleed tubes extending radially outward from the
carrier, each of the plurality of bleed tubes is configured to
receive bleed air.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 is a schematic of an exemplary gas turbine engine;
FIG. 2 is a schematic cross-sectional view of a portion of a rotor
impeller assembly that may be used with the gas turbine engine
shown in FIG. 1;
FIG. 3 is a rear perspective view of a portion of the rotor
impeller assembly shown in FIG. 2; and
FIG. 4 is a front perspective view of a portion of the rotor
impeller assembly shown in FIG. 2.
DETAILED DESCRIPTION OF THE INVENTION
FIG. 1 is a schematic illustration of a gas turbine engine 10.
Engine 10 includes, in serial axial flow communication about a
longitudinal centerline axis 12, a fan 14, a booster 16, a high
pressure compressor 18, and a combustor 20, a high pressure turbine
22, and a low pressure turbine 24. High pressure turbine 22 is
drivingly connected to high pressure compressor 18 with a first
rotor shaft 26, and low pressure turbine 24 is drivingly connected
to both booster 16 and fan 14 with a second rotor shaft 28, which
is disposed within first shaft 26. In one exemplary embodiment, the
gas turbine engine is an GE90 available from General Electric
Company, Cincinnati, Ohio.
In operation, air flows through fan 14, booster 16, and high
pressure compressor 18, being pressurized by each component in
succession. The highly compressed air is delivered to combustor 20.
Airflow from combustor 20 drives turbines 22 and 24 before exiting
gas turbine engine 10.
FIG. 2 is a schematic cross-sectional view of a portion of high
pressure compressor 18 including a rotor impeller assembly 30. FIG.
3 is a rear perspective view of a portion of rotor impeller
assembly 30 shown in FIG. 2. FIG. 4 is a front perspective view of
a portion of rotor impeller assembly 30 shown in FIG. 2. High
pressure turbine 22 includes a rotor assembly 32 that includes at
least one rotor 34. Rotor 34, as described in more detail below,
may be formed by one or more rotor disks 36. A plurality of blades
46 extend radially outward from an outer rim 48 of disk 36 and each
disk 36 extends circumferentially around rotor assembly 32. Each
row of blades 46 are sometimes referred to as a turbine stage.
In the exemplary embodiment, rotor impeller assembly 30, which is
described in greater detail below, extends circumferentially around
shaft 28 and is coupled to at least one rotor disk 36. In the
exemplary embodiment, rotor impeller assembly 30 is coupled between
stage seven and stage eight of rotor blade 36. Additionally, a
tubular air duct 34 that is defined at least partially between
disks 36 and shaft 28 and extends axially between, and is coupled
in flow communication to, rotor impeller assembly 30 for admitting
bleed air 132 from compressor 18. Bleed air 132 is channeled into
rotor impeller assembly 30 and is then ducted downstream to
facilitate cooling high pressure turbine blades 46 or pressurize a
downstream sump (not shown).
In the exemplary embodiment, rotor impeller assembly 30 includes a
carrier 60, a plurality of bleed tubes 62, and a coupling nut 64.
In the exemplary embodiment, carrier 60 includes a coupling portion
66, and a tube carrier portion 68, and an intermediate portion 70
extending generally radially therebetween and radially outward form
coupling portion 66. Carrier 60 also includes an outer surface 72,
an inner surface 74, and a body 76 extending therebetween. Body 76
has a low profile design such that it may be positioned radially
inward from rotor disks 36. Additionally, the design of body 76
facilitates reducing the weight of the rotor assembly 32 and
allowing a desired placement of rotor impeller assembly 30 within
engine 10.
Tube carrier portion 68 includes a plurality of openings 78 equally
circumferentially spaced around carrier 60. Each opening 78 extends
between outer surface 72 through a recess 80 within inner surface
74. Each recess 80 has a forward wall 82, and an aft wall 84 and a
support wall 86 extending therebetween. Openings 78 and recesses 80
are both configured to receive one bleed tube 62 there through. In
the exemplary embodiment, each bleed tubes 62 is removably fastened
to body 76 and is oriented substantially perpendicularly to axis of
rotation 28 (shown in FIG. 1). In one embodiment, a locking snap
ring 88 secures each bleed tube 62 with recess 80 and adjacent body
76. In alternative embodiments, bleed tubes 62 are coupled to rotor
impeller assembly 30 by any means that allows it to function as
described herein.
Each bleed tube 62 includes a first end 90, a coupling end 92, and
a body 94 extending therebetween and extends radially outward from
carrier 60 and are circumferentially spaced around carrier 60. In
the exemplary embodiment, each bleed tube 62 has an inner tubular
body 95 configure to act as a damper. Each bleed tube 62 has a
length 96 measured between first end 90 and coupling end 92, and an
outer diameter 98 measured at coupling end 92. In the exemplary
embodiment, each bleed tube 62 tapers from coupling end 92 towards
first end 90. An inner bore 100 extends throughout bleed tube body
94 and body 95 and is in flow communication with opening 78 and air
duct 34. Bleed tubes 62 are configured to extend between adjacent
disks 36 such that bleed tubes 62 are not in contact with disks
36.
In the exemplary embodiment, carrier 60 is coupled to disk 36 at
stage seven by an annular coupling nut 64. In the exemplary
embodiment, disk 36 includes a radially outer rim 38, a radially
inner hub 40, and an integral web 42 extending generally radially
therebetween and radially inward from a respective blade dovetail
slot 44. Additionally, disk 36 includes a mounting arm 120
extending radially inward from hub 40 towards shaft 26. Mounting
arm 120 includes an arm portion 122 extending radially and axially
inward toward shaft 28 and an attachment portion 124 extending
forward and substantially parallel to shaft 26. Mounting arm 120 is
flexible and as such facilitates reducing the displacement effects
on disk 36 during engine operation stress. In the exemplary
embodiment, rotor impeller assembly 30 is coupled to disk
attachment portion 124 by one annular coupling nut 64 and is
coupled to carrier coupling portion 66 by threaded engagement.
Coupling nut 64 extends circumferentially around carrier 60 such
that attachment portion 124 is secured between coupling nut 64 and
carrier coupling portion 66. Coupling nut 64 facilitates
positioning rotor impeller assembly 30 without utilizing bolts
and/or bolt holes in either carrier 60 or mounting arm 120.
Furthermore, coupling nut 64 is positionable radially inward from
mounting arm 120. When rotor impeller assembly 30 is coupled to
mounting arm 120 by coupling nut 64, a piston ring seal 128 seals a
sealing portion 130 on intermediate portion 70 seals carrier inner
portion 74 against air duct 34. Impeller assembly 30 is in sealing
engagement with air duct 34 such that bleed air 132 is permitted to
flow aftward above air duct 34. In an alternative embodiment, bleed
132 is permitted to flow both forward and aftward above air duct
34.
The above-described rotor impeller assembly is cost-effective and
highly reliable. The rotor impeller assembly includes a low profile
carrier that is configured to facilitate positioning the rotor
impeller assembly at an optimum stage for pressure and temperature.
Because the rotor impeller assembly utilizes a coupling nut in
threaded engagement with the carrier, neither the carrier nor the
disk require bolts and/or bolt holes. Accordingly, the rotor
impeller assembly thus facilitates reducing rotor assembly weight,
manufacturing costs, and disk wear. As a result, the rotor impeller
assembly facilitates extending a useful life of the turbine rotor
assembly in a cost-effective and reliable manner.
Exemplary embodiments of rotor assemblies and rotor impeller
assemblies are described above in detail. The rotor assemblies are
not limited to the specific embodiments described herein, but
rather, components of each assembly may be utilized independently
and separately from other components described herein. For example,
each rotor impeller assembly component can also be used in
combination with other cooling components and with other rotor
assemblies.
While the invention has been described in terms of various specific
embodiments, those skilled in the art will recognize that the
invention can be practiced with modification within the spirit and
scope of the claims.
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